US10906659B2 - Structured panel with structural reinforcement(s) - Google Patents

Structured panel with structural reinforcement(s) Download PDF

Info

Publication number
US10906659B2
US10906659B2 US15/943,963 US201815943963A US10906659B2 US 10906659 B2 US10906659 B2 US 10906659B2 US 201815943963 A US201815943963 A US 201815943963A US 10906659 B2 US10906659 B2 US 10906659B2
Authority
US
United States
Prior art keywords
skin
panel
rib
baffle
trajectory
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US15/943,963
Other languages
English (en)
Other versions
US20190300188A1 (en
Inventor
Mark R. Gurvich
Georgios S. Zafiris
Jeffrey A. Anderson
Jose S. Alonso-Miralles
Milan Mitrovic
Terry Muy
George Hoehn
Timothy Olson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rohr Inc
Original Assignee
Rohr Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rohr Inc filed Critical Rohr Inc
Priority to US15/943,963 priority Critical patent/US10906659B2/en
Assigned to ROHR, INC. reassignment ROHR, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: OLSON, TIMOTHY, ANDERSON, JEFFREY A., HOEHN, GEORGE, MUY, TERRY, ZAFIRIS, GEORGIOS S., MITROVIC, MILAN, ALONSO-MIRALLES, JOSE S., GURVICH, MARK R.
Priority to EP19166905.0A priority patent/EP3553771B1/de
Priority to CN201910265943.XA priority patent/CN110341931A/zh
Publication of US20190300188A1 publication Critical patent/US20190300188A1/en
Application granted granted Critical
Publication of US10906659B2 publication Critical patent/US10906659B2/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings or cowlings
    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/162—Selection of materials
    • G10K11/168—Plural layers of different materials, e.g. sandwiches
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This disclosure relates generally to structured panels and, more particularly for example, to a structured panel that attenuates sound generated by a gas turbine engine for an aircraft propulsion system.
  • Acoustic panels may be used in various applications to attenuate noise.
  • An acoustic panel for example, may be configured with a nacelle of an aircraft propulsion system to attenuate noise generated by a gas turbine engine.
  • Such an acoustic panel typically includes a honeycomb core connected between a perforated face skin and a solid, non-perforated back skin.
  • the honeycomb core includes a plurality of resonating chambers. These resonating chambers are tuned by selecting a desired chamber length and, thus, core thickness that corresponds to a specific target frequency of noise to be attenuated. Increasing the core thickness, for example, will typically tune the resonating chambers for attenuating lower frequency noise. Conversely, decreasing the core thickness will typically tune the resonating chambers for attenuating higher frequency noise.
  • a panel for attenuating noise.
  • This panel includes a perforated first skin, a second skin and a core.
  • the core forms a plurality of cavities vertically between the perforated first skin and the second skin.
  • the core includes an array of corrugations that include a first baffle, a second baffle and a first septum.
  • the cavities include a first cavity formed longitudinally between the first baffle and the second baffle.
  • the first cavity is fluidly coupled with perforations in the first skin.
  • the first septum extends from the first skin and the first baffle to the second skin and the second baffle.
  • the first septum divides the first cavity into fluidly coupled sub-cavities.
  • At least one element of the panel includes at least one first rib and at least one second rib.
  • the first rib extends along a first trajectory and the second rib extends along a second trajectory that is non-parallel with the first trajectory.
  • another panel for attenuating noise.
  • This panel includes a plurality of panel elements, which elements include a perforated first skin, a second skin and a core. At least one of the panel elements is configured with or otherwise includes a network of interconnected ribs.
  • the core forms a plurality of cavities vertically between the perforated first skin and the second skin.
  • the core includes an array of corrugations that include a first baffle, a second baffle and a first septum.
  • the cavities include a first cavity formed longitudinally between the first baffle and the second baffle.
  • the first cavity is fluidly coupled with perforations in the first skin.
  • the first septum extends from the first skin and the first baffle to the second skin and the second baffle. The first septum divides the first cavity into fluidly coupled sub-cavities.
  • still another panel for attenuating noise.
  • This panel includes a perforated first skin, a second skin and a core.
  • the core forms a plurality of cavities vertically between the perforated first skin and the second skin.
  • the core includes an array of corrugations that include a first baffle, a second baffle and a first septum.
  • the cavities include a first cavity formed longitudinally between the first baffle and the second baffle.
  • the first cavity is fluidly coupled with perforations in the first skin.
  • the first septum extends from the first skin and the first baffle to the second skin and the second baffle.
  • the first septum divides the first cavity into fluidly coupled sub-cavities.
  • At least one element of the core is configured with or otherwise includes a network of interconnected ribs.
  • the first trajectory may be offset from the second trajectory by an acute angle.
  • the first trajectory may be perpendicular to the second trajectory.
  • the first rib may run into the second rib.
  • the first rib may be discrete from the second rib.
  • the element of the panel may also include at least one third rib.
  • the third rib may extend along a third trajectory that may be non-parallel with the first trajectory.
  • the third trajectory may be parallel with the second trajectory.
  • the second rib and the third rib may each be coincident with the first rib.
  • the element of the panel may also include a fourth rib.
  • the fourth rib may extend along a fourth trajectory that may be non-parallel with the second trajectory.
  • the first rib and the fourth rib may each intersect with the second rib and the third rib.
  • the element of the panel may be configured as or otherwise include an element of the core.
  • the element of the panel may be configured as or otherwise include the first baffle.
  • the element of the panel may be configured as or otherwise include the septum.
  • the element of the panel may be configured as or otherwise include the first skin.
  • the element of the panel may be configured as or otherwise include the second skin.
  • the core may also include a first wall and a second wall.
  • the first cavity may be formed laterally between the first wall and the second wall.
  • the element of the panel may be configured as or otherwise include the first wall.
  • the core may be configured from or otherwise include composite material.
  • the panel may be configured as a panel for a nacelle of an aircraft propulsion system.
  • FIG. 1 is a perspective schematic illustration of a structured panel, in accordance with various embodiments
  • FIG. 2 is a first side sectional illustration of a portion of the structured panel, in accordance with various embodiments
  • FIG. 3 is a perspective illustration of a cellular core of the structured panel portion, in accordance with various embodiments.
  • FIG. 4 is a second side sectional illustration of the structured panel portion, in accordance with various embodiments.
  • FIG. 5 is a partial enlarged view of the structured panel portion of FIG. 2 , in accordance with various embodiments;
  • FIG. 6 is a first side sectional illustration of a portion of another structured panel, in accordance with various embodiments.
  • FIG. 7 is an illustration of a portion of a structured panel element configured with a structural reinforcement, in accordance with various embodiments
  • FIG. 8 is an illustration of a portion of a structured panel element configured with another structural reinforcement, in accordance with various embodiments.
  • FIG. 9 is an illustration of a portion of a structured panel element configured with another structural reinforcement, in accordance with various embodiments.
  • FIG. 10 is an illustration of a portion of a structured panel element configured with another structural reinforcement, in accordance with various embodiments.
  • FIG. 11 is an illustration of a portion of a structured panel element configured with still another structural reinforcement, in accordance with various embodiments.
  • FIG. 12 is an illustration of a structured panel element configured with a single structural reinforcement, in accordance with various embodiments.
  • FIG. 13 is an illustration of a structured panel element configured with a plurality of structural reinforcements, in accordance with various embodiments
  • FIG. 14 is a sectional illustration of a portion of a septum configured with a structural reinforcement rib, in accordance with various embodiments
  • FIG. 15 is a sectional illustration of a portion of another septum configured with a structural reinforcement rib, in accordance with various embodiments
  • FIG. 16 is a sectional illustration of a portion of still another septum configured with a structural reinforcement rib, in accordance with various embodiments
  • FIGS. 17-19 are first side sectional illustrations of alternative structural panels having structural reinforcements configured with its wall, in accordance with various embodiments.
  • FIG. 20 is a section illustration of a portion of a structured panel element configured with a plurality of structural reinforcement ribs, in accordance with various embodiments.
  • FIG. 21 is an illustration of another structured panel element configured with a structural reinforcement, in accordance with various embodiments.
  • the present disclosure includes structured panels such as, but not limited to, acoustic panels for attenuating sound; e.g., noise.
  • Each structured panel may include one or more structural reinforcements, such as rib structures, for increasing rigidity, strength, stability (i.e., resistance to buckling) and/or other metrics of structural integrity of that panel.
  • structural reinforcements such as rib structures
  • the following disclosure will first describe a general panel configuration without structural reinforcements and then describe how one or more structural reinforcements may be added to one or more elements (e.g., components) of the panel to increase rigidity, strength, stability and/or other metrics of structural integrity of that panel.
  • FIG. 1 is a partial, perspective block diagram illustration of an acoustic panel 100 for attenuating noise.
  • This acoustic panel 100 may be configured to attenuate noise generated by an aircraft propulsion system such as, for example, a turbofan propulsion system or a turbojet propulsion system.
  • the acoustic panel 100 may be configured with a nacelle of the propulsion system.
  • the acoustic panel 100 may be configured as or with an inner or outer barrel, a translating sleeve of a thrust reverser, a blocker door, etc.
  • the acoustic panel 100 may be configured with another component/structure of the aircraft such as its fuselage or a wing.
  • the acoustic panel 100 may be configured to also or alternatively attenuate aircraft related noise other than that generated by the propulsion system.
  • the acoustic panel 100 of the present disclosure may alternatively be configured for non-aircraft applications.
  • the acoustic panel 100 extends longitudinally along an x-axis.
  • the acoustic panel 100 extends laterally along a y-axis.
  • the acoustic panel 100 extends vertically along a z-axis.
  • the term “vertical” is used herein to describe a depthwise panel direction and is not limited to a gravitational up/down direction.
  • the x-y plane is shown as a generally flat plane. However, in other embodiments, the x-y plane and, thus, the acoustic panel 100 may be curved and/or follow an undulating geometry.
  • the x-y plane and, thus, the acoustic panel 100 may be arcuate, cylindrical or conical with or without radial undulations.
  • the vertical direction may change at different locations along the x-y plane; e.g., the vertical direction may be a radial direction for a cylindrical or conical acoustic panel.
  • the acoustic panel 100 includes a perforated first (e.g., face) skin 102 , a solid non-perforated second (e.g., back) skin 104 and a cellular core 106 .
  • the cellular core 106 is disposed and extends vertically between the first skin 102 and the second skin 104 .
  • the cellular core 106 is also connected to the first skin 102 and the second skin 104 .
  • the cellular core 106 may be fused, adhered, welded, brazed and/or otherwise bonded to the first skin 102 and/or the second skin 104 .
  • the cellular core 106 may also or alternatively be mechanically fastened to the first skin 102 and/or the second skin 104 .
  • the cellular core 106 may be formed integral with the first skin 102 and/or the second skin 104 as a monolithic body using, for example, additive manufacturing. However, the present disclosure is not limited to any particular manufacturing methods.
  • the first skin 102 may be configured as a relatively thin sheet or layer of material that extends longitudinally and laterally along the x-y plane.
  • This first skin material may include, but is not limited to, a polymer, a fiber reinforced composite (e.g., fiberglass composite, carbon fiber composite, aramid fiber composite, composite reinforced by any combination of glass, carbon, aramid or other fibers, etc.), metal, alloys, metal matrix composite, ceramic, or ceramic matrix composite, or a combination thereof.
  • the first skin 102 has a vertical thickness 108 that extends vertically between opposing side surfaces 110 and 112 .
  • the first skin 102 includes a plurality of perforations 114 ; e.g., apertures such as through-holes (see also FIG. 1 ). Each of these perforations 114 extends generally vertically through the first skin 102 between its side surfaces 110 and 112 .
  • the perforations 114 may be non-uniform through the thickness 108 and/or may be non-perpendicular to the side surfaces 110 and/or 112 .
  • the second skin 104 may be configured as a relatively thin sheet or layer of (e.g., continuous and uninterrupted) material that extends longitudinally and laterally along the x-y plane (see FIG. 1 ).
  • This second skin material may include, but is not limited to, a polymer, a fiber reinforced composite (e.g., fiberglass composite, carbon fiber composite, aramid fiber composite, composite reinforced by any combination of glass, carbon, aramid or other fibers, etc.), metal, alloys, metal matrix composite, ceramic, or ceramic matrix composite, or a combination thereof.
  • the second skin material may be the same as or different than the first skin material.
  • the second skin 104 has a vertical thickness 116 that extends vertically between opposing side surfaces 118 and 120 .
  • This vertical thickness 116 may be substantially equal to or different (e.g., greater or less) than the vertical thickness 108 of the first skin 102 .
  • the thickness 108 of the first skin 102 and/or the thickness 116 the second skin 104 may be uniform or non-uniform along the x-y plane.
  • the cellular core 106 extends longitudinally and laterally along the x-y plane.
  • the cellular core 106 has a vertical thickness 122 that extends vertically between opposing core sides, which sides are respectively abutted against the first skin 102 and the second skin 104 .
  • the vertical thickness 122 may be substantially greater than the vertical thicknesses 108 and 116 of the first skin 102 and/or the second skin 104 , respectively.
  • the vertical thickness 122 for example, may be at least ten to forty times (10-40 ⁇ ), or more, greater than the vertical thicknesses 108 , and 116 ; however, the acoustic panel 100 of the present disclosure is not limited to such an exemplary embodiment.
  • the cellular core 106 includes a plurality of solid non-perforated walls 124 (e.g., cavity sidewalls) and one or more arrays of corrugations 126 .
  • the walls 124 and corrugations 126 are arranged together to configure the cellular core 106 as an open cavity (e.g., open cell) structure.
  • This open cavity structure forms a plurality of cavities 128 (each including divided sub-cavities 128 A and 128 B) vertically between the first skin 102 and the second skin 104 .
  • Each of these cavities 128 may be fluidly coupled with one or more respective perforations 114 in the first skin 102 (see FIG. 2 ).
  • each of the walls 124 has a length that extends longitudinally along the x-axis.
  • Each of the walls 124 has a thickness that extends laterally along the y-axis.
  • each of the walls 124 has a height that extends vertically between the first skin 102 and the second skin 104 .
  • Each of the walls 124 is, at least, partially (or completely) connected to or otherwise engaged with the first skin 102 and/or the second skin 104 .
  • Each of the exemplary walls 124 of FIG. 4 is orientated substantially perpendicular to the first skin 102 and the second skin 104 ; e.g., at a ninety-degree angle to the skins 102 and 104 .
  • one or more of the walls 124 may be angularly offset from the first skin 102 and/or the second skin 104 by a non-ninety-degree angle; e.g., an acute included angle or an obtuse angle.
  • the walls 124 are arranged generally parallel with one another; see also FIG. 3 .
  • the walls 124 are laterally spaced from one another along the y-axis so as to respectively form the cavities 128 between the walls 124 .
  • Each of the walls 124 shown in FIG. 4 therefore respectively forms lateral sides of adjacent cavities 128 on either side of the respective wall 124 .
  • Each of the walls 124 thereby also fluidly separates those cavities 128 on either side of the wall 124 .
  • each of the corrugations 126 in each array are disposed and extend laterally between a laterally adjacent pair of the walls 124 ; see also FIG. 4 .
  • Each of the corrugations 126 includes a solid non-perforated baffle 130 and a porous (e.g., perforated) septum 132 .
  • one or more or each of the corrugations 126 includes only porous (e.g. perforated) septa 132 , or only solid non-perforated baffles 130 in an alternating periodic or non-periodic pattern along the y-axis or the x-axis or both.
  • the baffle 130 has a width extending laterally between opposing lateral sides. These lateral sides are, at least, partially (or completely) connected to or otherwise engaged with a respective laterally adjacent pair of the walls 124 .
  • the baffle 130 has a length extending vertically and longitudinally between opposing top and bottom ends 134 and 136 . Note, the terms “top” and “bottom” are used above to describe ends of the baffle 130 as situated in the drawings and are not intended to limit the baffle 130 or the acoustic panel 100 to such an exemplary gravitational orientation.
  • the septum 132 has a width extending laterally between opposing lateral sides. These lateral sides are connected to or otherwise engaged with a respective laterally adjacent pair of the walls 124 .
  • the septum 132 has a length extending vertically and longitudinally between opposing top and bottom ends 138 and 140 . Note, the terms “top” and “bottom” are used above to describe ends of the septum 132 as situated in the drawings and are not intended to limit the septum 132 or the acoustic panel 100 to such an exemplary gravitational orientation.
  • the septum 132 includes one or more perforations 142 .
  • the perforations 142 are configured as through holes.
  • the perforations 142 may be formed by interconnected pores in the septum 132 where the septum material, for example, has an open cell porous structure.
  • the top end 134 of the baffle 130 is connected, at least, partially (or completely) to or otherwise engaged with the first skin 102 .
  • This top end 134 is also longitudinally connected to the top end 138 of the septum 132 at an interface 144 between the baffle 130 and the septum 132 .
  • the bottom end 136 of the baffle 130 is connected to or otherwise engaged with the second skin 104 .
  • This bottom end 136 is also longitudinally connected to the bottom end 140 of a septum 132 of an adjacent one of the corrugations 126 at an interface 146 .
  • the baffle 130 extends vertically between the first skin 102 and the second skin 104 and longitudinally between the septums 132 .
  • the baffle 130 is therefore angularly offset from the first skin 102 and the second skin 104 by an included angle 148 ; e.g., between 30-60 degrees.
  • This angle 148 is an acute angle such as, but not limited to, about forty-five degrees (45°).
  • the top end 138 of the septum 132 is, at least, partially (or completely) connected to or otherwise engaged with the first skin 102 .
  • This top end 138 is also longitudinally connected to the top end 134 of the baffle 130 as described above.
  • the bottom end 140 of the septum 132 is, at least, partially (or completely) connected to or otherwise engaged with the second skin 104 .
  • This bottom end 140 is also longitudinally connected to the bottom end 136 of a baffle 130 of an adjacent one of the corrugations 126 at an interface; e.g., the interface 146 .
  • the septum 132 extends vertically between the first skin 102 and the second skin 104 and longitudinally between the baffles 130 .
  • the septum 132 is therefore angularly offset from the first skin 102 and the second skin 104 by an included angle 150 ; e.g., between 30-60 degrees.
  • This angle 150 may be an acute angle such as, but not limited to, about forty-five degrees (45°).
  • the angle 150 may be substantially equal to the angle 148 as shown in FIG. 5 .
  • the angle 150 may be different from the angle 148 ; e.g., a larger or smaller acute angle, or a right angle.
  • the angle 150 may be about ninety degrees and the angle 148 may be about forty-five degrees as shown in FIG. 6 .
  • each of the cavities 128 extends longitudinally between and is formed by a longitudinally adjacent pair of the baffles 130 .
  • Each septum 132 is disposed within and divides a respective one of the cavities 128 into fluidly coupled sub-cavities 128 A and 128 B. More particularly, the perforations 142 in the septum 132 fluidly couple the sub-cavities 128 A and 128 B together.
  • Each of the cavities 128 forms a resonance chamber 152 .
  • a length 154 of the resonance chamber 152 extends diagonally (e.g., longitudinally and vertically) between the first skin 102 and the second skin 104 and through a respective one of the septums 132 .
  • the length 154 of the resonance chamber 152 therefore is longer than the vertical thickness 122 of the cellular core 106 . This enables noise attenuation of relatively low frequency noise without increasing the vertical thickness 152 of the cellular core 106 and, thus, a vertical thickness of the acoustic panel 100 .
  • each resonance chamber 152 may receive noise waves through the perforations 114 in the first skin 102 .
  • the resonance chamber 152 may reverse the phase of one or more frequencies of those sound waves using known acoustic reflection principles and subsequently direct the reverse phase sound waves out of the acoustic panel 100 through the perforations 114 to destructively interfere with other incoming noise waves.
  • the cellular core 106 may be constructed from any suitable material or materials.
  • the cellular core 106 may be constructed from a polymer, a fiber reinforced composite (e.g., fiberglass composite, carbon fiber composite, aramid fiber composite, composite reinforced by any combination of glass, carbon, aramid or other fibers), metal, alloys, metal matrix composite, ceramic, or ceramic matrix composite, or a combination thereof.
  • One or more of components of the cellular core 106 may be constructed from the same or a like material.
  • one or more of the components of the cellular core 106 may be constructed from a different material than one or more of the other components of the cellular core 106 .
  • the cellular core 106 may be constructed from the same material(s) as the first skin 102 and/or the second skin 104 , or a different material or materials.
  • one or more elements of the acoustic panel 100 may be configured with one or more structural reinforcements. These structural reinforcements are provided to increase rigidity, stability, strength and/or structural integrity of the corresponding element(s) as well as the acoustic panel 100 as a whole. Examples of the one or more elements include, but are not limited to: (A) one, some or each of the baffles 130 ; (B) one, some or each of the septums 132 ; and (C) one, some or each of the walls 124 .
  • One or more structural reinforcements may also or alternatively be configured with one or more other elements of the acoustic panel 100 .
  • one or more structural elements may be configured with the first skin 102 and/or the second skin 104 .
  • FIG. 7 illustrates a portion of an acoustic panel element 156 A configured with a first exemplary structural reinforcement 158 A.
  • the acoustic panel element 156 A can be one or more of the walls 124 , or the corrugations 126 , or both, or combinations thereof. In another exemplary case the acoustic panel element 156 A can be the first skin 102 , or the second skin 104 , or both, or combinations thereof in part or in their entirety.
  • the structural reinforcement 158 A is configured as or otherwise includes a network of interconnected ribs. In particular, the structural reinforcement 158 A of FIG.
  • each rib 160 A, 162 A may be a stamped and/or otherwise formed element (e.g., protrusion) that projects out from a respective surface/side of the acoustic panel element 156 A.
  • the first rib 160 A extends along a first trajectory 164 A and the second rib 162 A extends along a second trajectory 166 A.
  • the term “trajectory” may describe a centerline that follows along a length of a feature, where that length is greater than other dimensions (e.g., a width and/or a thickness) of the feature.
  • the first trajectory 164 A and the second trajectory 166 A are straight-line trajectories; however, in other embodiments, one or both of these trajectories 164 A and 166 A may alternatively be curved or otherwise convoluted line trajectories.
  • the first trajectory 164 A of the first rib 160 A is non-parallel with the second trajectory 166 A of the second rib 162 A.
  • the first trajectory 164 A and the first rib 160 A of FIG. 7 for example, are perpendicular and coincident with the second trajectory 166 A and the second rib 162 A.
  • an included angle between the first and the second trajectories 164 B and 166 B and ribs 160 B and 162 B of the structural reinforcement 158 B on the acoustic panel element 156 B may be acute (or obtuse) as shown in FIG. 8 for example.
  • the first rib 160 A intersects and thereby runs into the second rib 162 A.
  • the first rib 160 A of FIG. 7 bisects the second rib 162 A and the second rib 162 A bisects the first rib 160 A.
  • the first rib 160 A may serve to minimize risk of bending/buckling of the acoustic panel element 156 A portion along an axis running parallel or acutely angled relative to its first trajectory 164 A.
  • the second rib 162 A may serve to minimize risk of bending/buckling of the acoustic panel element 156 A portion along an axis running parallel or acutely angled relative to its second trajectory 166 A.
  • FIG. 9 illustrates another acoustic panel element 156 C portion configured with a second exemplary structural reinforcement 168 .
  • This structural reinforcement 168 includes the first rib 160 C and a plurality of the second ribs 162 C; however, a similar arrangement may be made with a single second rib 162 C and a plurality of the first ribs 160 C in other embodiments.
  • the terms “first” and “second” are used to describe the ribs in order of introduction; thus, the first ribs 160 C may include a first rib 160 C, a second rib 160 C, a third rib 160 C, etc.
  • the second ribs 162 C may include a first rib 162 C, a second rib 162 C, a third rib 160 C, etc.
  • the second trajectories 166 C of the second ribs 162 C may be parallel (or substantially parallel; e.g., up to one to ten degrees offset) with one another and, thus, non-parallel with the first trajectory 164 C.
  • the included angles between the first and the second trajectories 164 C and 166 C and ribs 160 C and 162 C of the structural reinforcement 168 on the acoustic panel element 156 C may be 90°, or acute, or obtuse.
  • the first rib 160 C may bisect each or some of the second ribs 162 C.
  • FIG. 10 illustrates another acoustic panel element 156 D portion configured with a third exemplary structural reinforcement 170 .
  • This structural reinforcement 170 includes a plurality of the first ribs 160 D and a plurality of the second ribs 162 D.
  • first and second are used to describe the ribs in order of introduction; thus, the first ribs 160 D may include a first rib 160 D, a second rib 160 D, a third rib 160 D, etc. and the second ribs 162 D may include a first rib 162 D, a second rib 162 D, a third rib 160 D, etc.
  • the first trajectories 164 D of the first ribs 160 D may be parallel (or substantially parallel; e.g., up to one to five degrees offset) with one other.
  • the second trajectories 166 D of the second ribs 162 D may be parallel with one another and, thus, non-parallel with the first trajectories 164 D.
  • This configuration of first and second ribs 160 D and 162 D is in the form of a grid.
  • Each of the first ribs 160 D may intersect each or some of the second ribs 162 D, and each of the second ribs 162 D may intersect each or some of the first ribs 160 D.
  • the included angles between the first and the second trajectories 164 D and 166 D and ribs 160 D and 162 D of the structural reinforcement 170 on the acoustic panel element 156 D may be 90°, acute, or obtuse.
  • the first ribs 160 A, 160 B, 160 C, 160 D (generally referred to as “ 160 ”) run right-and-left and the second ribs 162 A, 162 B, 162 C, 162 D (generally referred to as “ 162 ”) run up-and-down relative to the acoustic panel element 156 A, 156 B, 156 C, 156 D (generally referred to as “ 156 ”) portion.
  • any of these exemplary structural reinforcements may be reoriented such that the second ribs 162 run right-and-left and the first ribs 160 run up-and-down relative to the acoustic panel element 156 portion.
  • any of the exemplary structural reinforcements may be reoriented such that the first and the second ribs 160 and 162 run diagonally or along another angle relative to the acoustic panel element 156 portion.
  • the first rib 160 E runs along the first trajectory 164 E diagonally from a top-left end to a bottom-right end.
  • the second rib 162 E runs along the second trajectory 166 E diagonally from a top-right end to a bottom-left end.
  • a respective acoustic core element 156 F may be configured with a single structural reinforcement 172 (e.g., any of the afore-described structural reinforcements 158 A, or 158 B, or 168 , or 170 ), for example as shown in FIG. 12 .
  • a respective acoustic core element 156 G may be configured with a plurality of discrete structural reinforcements 174 A-D (e.g., any of the afore-described structural reinforcements 158 A, or 158 B, or 168 , or 170 ), for example as shown in FIG. 13 .
  • the 12 and 13 may include respective ribs 160 F, G and 162 F, G, respectively.
  • the ribs 160 G and 162 G of the structural reinforcement 174 A are discrete (e.g., do not intersect or touch) any of the other structural reinforcements 174 B-D or their respective ribs.
  • one, some or each of the ribs (e.g., 160 H, 162 H) of the structural reinforcement may be non-perforated, for example as shown in FIG. 14 .
  • one, some or each of the ribs (e.g., 160 I, 160 J, 162 I, 162 J) of the structural reinforcement may be perforated ( 142 B), for example as shown on the septums 132 B and 132 C in FIGS. 15 and 16 .
  • the perforations 142 may also be included on portions of the septum 132 C not occupied by (e.g., adjacent to and around) the ribs (e.g., 160 , 162 ), for example as shown in FIGS. 16 and 14 .
  • the structural reinforcements 180 A may be located (e.g., only vertically) between the corrugations 126 A and the first skin 102 A, for example as shown in FIG. 17 .
  • the structural reinforcements 180 B may be located (e.g., only vertically) between the corrugations 126 B and the second skin 104 B, for example as shown in FIG. 18 .
  • the structural reinforcements 180 C and 180 D may be located both (e.g., vertically) between the corrugations 126 C and the first skin 102 C as well as (e.g., vertically) between the corrugations 126 C and the second skin 104 C.
  • ribs of a structural reinforcement may be arranged on a common side of the acoustic panel portion as generally shown in the figures discussed above.
  • the ribs (e.g., 160 K, 162 K) of the acoustic panel element 156 K may be arranged on opposing sides of the acoustic panel portion, for example as shown in FIG. 20 .
  • the first skin 102 and/or the second skin 104 may each be configured with one or more of the structural reinforcements described above.
  • the skin 102 A, 104 A of FIG. 21 includes at least one structural reinforcement 182 , which includes at least one first rib 160 L and at least one second rib 162 L.
  • the perforations 114 through the first skin 102 A are not included on portions of the ribs 160 L and 162 L. In another embodiment the perforations 114 through the first skin 102 A are included on portions of the ribs 160 L and 162 L.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
US15/943,963 2018-04-03 2018-04-03 Structured panel with structural reinforcement(s) Active 2039-07-14 US10906659B2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US15/943,963 US10906659B2 (en) 2018-04-03 2018-04-03 Structured panel with structural reinforcement(s)
EP19166905.0A EP3553771B1 (de) 2018-04-03 2019-04-02 Strukturierte tafel mit struktureller verstärkung(en)
CN201910265943.XA CN110341931A (zh) 2018-04-03 2019-04-03 具有结构加强件的结构化面板

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/943,963 US10906659B2 (en) 2018-04-03 2018-04-03 Structured panel with structural reinforcement(s)

Publications (2)

Publication Number Publication Date
US20190300188A1 US20190300188A1 (en) 2019-10-03
US10906659B2 true US10906659B2 (en) 2021-02-02

Family

ID=66091981

Family Applications (1)

Application Number Title Priority Date Filing Date
US15/943,963 Active 2039-07-14 US10906659B2 (en) 2018-04-03 2018-04-03 Structured panel with structural reinforcement(s)

Country Status (3)

Country Link
US (1) US10906659B2 (de)
EP (1) EP3553771B1 (de)
CN (1) CN110341931A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11433990B2 (en) * 2018-07-09 2022-09-06 Rohr, Inc. Active laminar flow control system with composite panel
US12479201B2 (en) 2022-07-08 2025-11-25 Rohr, Inc. Forming pattern for cellular core by folding material

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11767776B2 (en) 2020-09-04 2023-09-26 The Boeing Company Propulsion flow path duct systems and methods
US12078125B2 (en) 2021-09-13 2024-09-03 Rohr, Inc. Low-frequency acoustic center body

Citations (68)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2333343A (en) 1937-04-22 1943-11-02 Armzen Company Method of making structural materials
US3011602A (en) 1959-07-13 1961-12-05 Lockheed Aircraft Corp Panel construction
US3025122A (en) 1960-11-25 1962-03-13 American Air Filter Co Mounting arrangement
US3341395A (en) 1962-12-03 1967-09-12 Solar Reflection Room Corp Lightweight structural panel
US3380206A (en) 1965-09-29 1968-04-30 Soundlock Corp Lay-in acoustical ceiling panel with flexible diaphragms
US3439774A (en) 1966-01-21 1969-04-22 Boeing Co Sound energy absorbing apparatus
US3507355A (en) 1969-05-22 1970-04-21 Rohr Corp Multi-layer face material for sound absorptive duct lining material
US3542152A (en) 1968-04-08 1970-11-24 Gen Electric Sound suppression panel
US3639106A (en) 1968-05-06 1972-02-01 Burnley Engineering Products L Acoustic panel
US3640357A (en) 1970-02-24 1972-02-08 Rolls Royce Acoustic linings
US3734234A (en) 1971-11-08 1973-05-22 Lockheed Aircraft Corp Sound absorption structure
FR2201010A5 (de) 1972-09-01 1974-04-19 Short Brothers & Harland Ltd
US3819007A (en) 1973-04-27 1974-06-25 Lockheed Aircraft Corp Controllable laminar sound absorptive structure
US3821999A (en) 1972-09-05 1974-07-02 Mc Donnell Douglas Corp Acoustic liner
US3831710A (en) 1973-01-24 1974-08-27 Lockheed Aircraft Corp Sound absorbing panel
US3848697A (en) 1972-07-04 1974-11-19 Aerospatiale Acoustic damping and cooling of turbojet exhaust ducts
US3850261A (en) 1973-03-01 1974-11-26 Gen Electric Wide band width single layer sound suppressing panel
US3910374A (en) 1974-03-18 1975-10-07 Rohr Industries Inc Low frequency structural acoustic attenuator
US3948346A (en) 1974-04-02 1976-04-06 Mcdonnell Douglas Corporation Multi-layered acoustic liner
US3969563A (en) 1969-08-28 1976-07-13 Hollis Sr Russell E Protective wall structure
US4189027A (en) 1976-08-19 1980-02-19 United Technologies Corporation Sound suppressor liners
US4240519A (en) 1979-07-02 1980-12-23 United Technologies Corporation Acoustical turbine engine tail pipe plug
US4859517A (en) 1987-03-16 1989-08-22 Hexcel Corporation Formable honeycomb panel
US5431980A (en) 1993-02-01 1995-07-11 Mccarthy; Daniel J. Formable cellular material with synclastic behavior
US5498462A (en) 1994-04-01 1996-03-12 Hexcel Corporation High thermal conductivity non-metallic honeycomb
US5634306A (en) 1991-11-06 1997-06-03 Riegelman; Harry M. Composite framing member construction for windows and doors
US5923003A (en) 1996-09-09 1999-07-13 Northrop Grumman Corporation Extended reaction acoustic liner for jet engines and the like
US5997985A (en) 1998-09-10 1999-12-07 Northrop Grumman Corporation Method of forming acoustic attenuation chambers using laser processing of multi-layered polymer films
US6598701B1 (en) 2000-06-30 2003-07-29 3M Innovative Properties Company Shaped microperforated polymeric film sound absorbers and methods of manufacturing the same
US6725541B1 (en) 2000-01-21 2004-04-27 Rolls-Royce Plc Flow directing element and a method of manufacturing a flow directing element
US6871725B2 (en) 2003-02-21 2005-03-29 Jeffrey Don Johnson Honeycomb core acoustic unit with metallurgically secured deformable septum, and method of manufacture
US6949282B2 (en) 2000-07-07 2005-09-27 Delphi Technologies, Inc. Contoured crushable composite structural members and methods for making the same
US7124856B2 (en) 2002-10-14 2006-10-24 Rolls-Royce Plc Acoustic liner for gas turbine engine
CN101649818A (zh) 2009-09-17 2010-02-17 秦皇岛耀华玻璃钢股份公司 隔音降噪型风力发电机机舱罩
US7784283B2 (en) 2006-05-03 2010-08-31 Rohr, Inc. Sound-absorbing exhaust nozzle center plug
US7814658B2 (en) 2003-11-20 2010-10-19 Otkrytoe Aktsionernoe Obschestvo “Kazansky Nauchno-Isledovatelsky Institut Aviatsionnoi Tekhnologii” Method for production of sandwich panels with zigzag corrugated core
US7878229B2 (en) 2002-03-26 2011-02-01 Ube Nitto Kasei Co., Ltd. Hollow structure plate, manufacturing method thereof, manufacturing device thereof, and sound absorbing structure plate
RU2413654C2 (ru) 2006-05-24 2011-03-10 Эйрбас Дойчланд Гмбх Многослойный элемент для звукопоглощающей внутренней обшивки транспортного средства, преимущественно самолета
US20110100747A1 (en) 2006-05-24 2011-05-05 Airbus Operations Gmbh Sandwich element for the sound-absorbing inner cladding of means of transport, especially for the sound-absorbing inner cladding of aircraft
US7959109B2 (en) 2008-07-02 2011-06-14 The Boeing Company Dual valve apparatus for aircraft engine ice protection and related methods
US7963362B2 (en) 2007-04-30 2011-06-21 Airbus Operations Sas Acoustic panel having a variable acoustic characteristic
US7971684B2 (en) 2007-02-20 2011-07-05 Airbus Operations Sas Acoustic panel
US8245815B2 (en) 2007-10-16 2012-08-21 Aircelle Cellular-core structure for an acoustic panel
US8336316B2 (en) 2008-11-11 2012-12-25 Rolls-Royce Plc Noise reduction device
US8413922B2 (en) 2007-12-21 2013-04-09 Creuzet Aeronautique Acoustic processing structure particularly adapted to the air inlet of an aircraft nacelle
US8449707B2 (en) 2002-01-28 2013-05-28 Innovative Composites Inc. Method of manufacturing a structural polymer core assembly
US8517309B2 (en) 2011-06-02 2013-08-27 Bell Helicopter Textron Inc. Integrally stiffened panel
US8544598B2 (en) 2011-08-22 2013-10-01 Snecma Soundproofing panel for turbomachine and turbomachine comprising such a panel
US20130266772A1 (en) 2004-06-15 2013-10-10 John S. Fujii Three-dimensional wood fiber structural composites
US20140034416A1 (en) 2011-04-20 2014-02-06 Dresser-Rand Company Multi-degree of freedom resonator array
US8646574B2 (en) 2009-11-23 2014-02-11 Aircelle Acoustic skin for an aircraft nacelle acoustic panel
US8684301B2 (en) 2008-04-30 2014-04-01 Airbus Operations S.A.S. Wave attenuation panel inserted between the motor and air inlet of an aircraft nacelle
US8733501B2 (en) 2011-12-13 2014-05-27 Airbus Operations Sas Method for producing an acoustic treatment panel
US8763751B2 (en) 2008-10-10 2014-07-01 Airbus Operations Gmbh Silencer for an auxiliary power unit of an aircraft
US8776946B2 (en) 2011-01-19 2014-07-15 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine exhaust cone
US8820477B1 (en) 2013-07-29 2014-09-02 The Boeing Company Acoustic panel
US20140349082A1 (en) 2013-05-21 2014-11-27 The Boeing Company Folded Core Panel
US20150110603A1 (en) 2013-10-17 2015-04-23 Rohr, Inc. Acoustic structural panel with slanted core
CN104723616A (zh) 2015-03-17 2015-06-24 西安交通大学 一种轻质正交波纹夹芯复合结构及其制备方法
US20150284945A1 (en) 2014-04-04 2015-10-08 The Boeing Company Pyramid waffle core structure and method of fabrication
US20150367953A1 (en) 2014-06-23 2015-12-24 Rohr, Inc. Acoustic liner
US20160312709A1 (en) 2015-01-29 2016-10-27 Rohr, Inc. Acoustic structural panel with herringbone core
US9704467B1 (en) 2016-04-15 2017-07-11 Rohr, Inc. Acoustic panel with corrugated baffles and septums
US20170225764A1 (en) * 2016-02-10 2017-08-10 Rohr, Inc. Structural, cellular core with corrugated support walls
US20170229106A1 (en) 2016-02-10 2017-08-10 Rohr, Inc. Acoustic panel with angled corrugated core structures
US20170301334A1 (en) 2016-04-15 2017-10-19 Rohr, Inc. Acoustic panel with vertical stiffeners
US20180142621A1 (en) 2016-11-18 2018-05-24 Rohr, Inc. Acoustic panel with sidewall stringers
US20180229829A1 (en) 2017-02-14 2018-08-16 Rohr, Inc. Method for forming a structural panel

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7721995B2 (en) * 2006-12-13 2010-05-25 The Boeing Company Rib support for wing panels
CN103118940B (zh) * 2010-07-20 2017-01-18 空中客车运作有限责任公司 具有至少一个主负荷承载蒙皮外壳和联接该主负荷承载蒙皮外壳的支撑结构的结构件以及具有这种结构件的流动体
US10040537B2 (en) * 2015-01-15 2018-08-07 The Boeing Company Laminate composite wing structures
EP3281861B1 (de) * 2016-08-11 2019-10-02 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Drehflügler mit einem rumpf mit mindestens einem strukturell versteiften paneel

Patent Citations (70)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2333343A (en) 1937-04-22 1943-11-02 Armzen Company Method of making structural materials
US3011602A (en) 1959-07-13 1961-12-05 Lockheed Aircraft Corp Panel construction
US3025122A (en) 1960-11-25 1962-03-13 American Air Filter Co Mounting arrangement
US3341395A (en) 1962-12-03 1967-09-12 Solar Reflection Room Corp Lightweight structural panel
US3380206A (en) 1965-09-29 1968-04-30 Soundlock Corp Lay-in acoustical ceiling panel with flexible diaphragms
US3439774A (en) 1966-01-21 1969-04-22 Boeing Co Sound energy absorbing apparatus
US3542152A (en) 1968-04-08 1970-11-24 Gen Electric Sound suppression panel
US3639106A (en) 1968-05-06 1972-02-01 Burnley Engineering Products L Acoustic panel
US3507355A (en) 1969-05-22 1970-04-21 Rohr Corp Multi-layer face material for sound absorptive duct lining material
US3969563A (en) 1969-08-28 1976-07-13 Hollis Sr Russell E Protective wall structure
US3640357A (en) 1970-02-24 1972-02-08 Rolls Royce Acoustic linings
US3734234A (en) 1971-11-08 1973-05-22 Lockheed Aircraft Corp Sound absorption structure
US3848697A (en) 1972-07-04 1974-11-19 Aerospatiale Acoustic damping and cooling of turbojet exhaust ducts
FR2201010A5 (de) 1972-09-01 1974-04-19 Short Brothers & Harland Ltd
GB1406844A (en) 1972-09-01 1975-09-17 Short Brothers & Harland Ltd Sound absorbing panels
US3821999A (en) 1972-09-05 1974-07-02 Mc Donnell Douglas Corp Acoustic liner
US3831710A (en) 1973-01-24 1974-08-27 Lockheed Aircraft Corp Sound absorbing panel
US3850261A (en) 1973-03-01 1974-11-26 Gen Electric Wide band width single layer sound suppressing panel
US3819007A (en) 1973-04-27 1974-06-25 Lockheed Aircraft Corp Controllable laminar sound absorptive structure
US3910374A (en) 1974-03-18 1975-10-07 Rohr Industries Inc Low frequency structural acoustic attenuator
US3948346A (en) 1974-04-02 1976-04-06 Mcdonnell Douglas Corporation Multi-layered acoustic liner
US4189027A (en) 1976-08-19 1980-02-19 United Technologies Corporation Sound suppressor liners
US4240519A (en) 1979-07-02 1980-12-23 United Technologies Corporation Acoustical turbine engine tail pipe plug
US4859517A (en) 1987-03-16 1989-08-22 Hexcel Corporation Formable honeycomb panel
US5634306A (en) 1991-11-06 1997-06-03 Riegelman; Harry M. Composite framing member construction for windows and doors
US5431980A (en) 1993-02-01 1995-07-11 Mccarthy; Daniel J. Formable cellular material with synclastic behavior
US5498462A (en) 1994-04-01 1996-03-12 Hexcel Corporation High thermal conductivity non-metallic honeycomb
US5923003A (en) 1996-09-09 1999-07-13 Northrop Grumman Corporation Extended reaction acoustic liner for jet engines and the like
US5997985A (en) 1998-09-10 1999-12-07 Northrop Grumman Corporation Method of forming acoustic attenuation chambers using laser processing of multi-layered polymer films
US6725541B1 (en) 2000-01-21 2004-04-27 Rolls-Royce Plc Flow directing element and a method of manufacturing a flow directing element
US6598701B1 (en) 2000-06-30 2003-07-29 3M Innovative Properties Company Shaped microperforated polymeric film sound absorbers and methods of manufacturing the same
US6949282B2 (en) 2000-07-07 2005-09-27 Delphi Technologies, Inc. Contoured crushable composite structural members and methods for making the same
US8449707B2 (en) 2002-01-28 2013-05-28 Innovative Composites Inc. Method of manufacturing a structural polymer core assembly
US7878229B2 (en) 2002-03-26 2011-02-01 Ube Nitto Kasei Co., Ltd. Hollow structure plate, manufacturing method thereof, manufacturing device thereof, and sound absorbing structure plate
US7124856B2 (en) 2002-10-14 2006-10-24 Rolls-Royce Plc Acoustic liner for gas turbine engine
US6871725B2 (en) 2003-02-21 2005-03-29 Jeffrey Don Johnson Honeycomb core acoustic unit with metallurgically secured deformable septum, and method of manufacture
US7814658B2 (en) 2003-11-20 2010-10-19 Otkrytoe Aktsionernoe Obschestvo “Kazansky Nauchno-Isledovatelsky Institut Aviatsionnoi Tekhnologii” Method for production of sandwich panels with zigzag corrugated core
US20130266772A1 (en) 2004-06-15 2013-10-10 John S. Fujii Three-dimensional wood fiber structural composites
US7784283B2 (en) 2006-05-03 2010-08-31 Rohr, Inc. Sound-absorbing exhaust nozzle center plug
RU2413654C2 (ru) 2006-05-24 2011-03-10 Эйрбас Дойчланд Гмбх Многослойный элемент для звукопоглощающей внутренней обшивки транспортного средства, преимущественно самолета
US20110100747A1 (en) 2006-05-24 2011-05-05 Airbus Operations Gmbh Sandwich element for the sound-absorbing inner cladding of means of transport, especially for the sound-absorbing inner cladding of aircraft
US7971684B2 (en) 2007-02-20 2011-07-05 Airbus Operations Sas Acoustic panel
US7963362B2 (en) 2007-04-30 2011-06-21 Airbus Operations Sas Acoustic panel having a variable acoustic characteristic
US8245815B2 (en) 2007-10-16 2012-08-21 Aircelle Cellular-core structure for an acoustic panel
US8413922B2 (en) 2007-12-21 2013-04-09 Creuzet Aeronautique Acoustic processing structure particularly adapted to the air inlet of an aircraft nacelle
US8684301B2 (en) 2008-04-30 2014-04-01 Airbus Operations S.A.S. Wave attenuation panel inserted between the motor and air inlet of an aircraft nacelle
US7959109B2 (en) 2008-07-02 2011-06-14 The Boeing Company Dual valve apparatus for aircraft engine ice protection and related methods
US8763751B2 (en) 2008-10-10 2014-07-01 Airbus Operations Gmbh Silencer for an auxiliary power unit of an aircraft
US8336316B2 (en) 2008-11-11 2012-12-25 Rolls-Royce Plc Noise reduction device
CN101649818A (zh) 2009-09-17 2010-02-17 秦皇岛耀华玻璃钢股份公司 隔音降噪型风力发电机机舱罩
US8646574B2 (en) 2009-11-23 2014-02-11 Aircelle Acoustic skin for an aircraft nacelle acoustic panel
US8776946B2 (en) 2011-01-19 2014-07-15 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine exhaust cone
US8955643B2 (en) 2011-04-20 2015-02-17 Dresser-Rand Company Multi-degree of freedom resonator array
US20140034416A1 (en) 2011-04-20 2014-02-06 Dresser-Rand Company Multi-degree of freedom resonator array
US8517309B2 (en) 2011-06-02 2013-08-27 Bell Helicopter Textron Inc. Integrally stiffened panel
US8544598B2 (en) 2011-08-22 2013-10-01 Snecma Soundproofing panel for turbomachine and turbomachine comprising such a panel
US8733501B2 (en) 2011-12-13 2014-05-27 Airbus Operations Sas Method for producing an acoustic treatment panel
US20140349082A1 (en) 2013-05-21 2014-11-27 The Boeing Company Folded Core Panel
US8820477B1 (en) 2013-07-29 2014-09-02 The Boeing Company Acoustic panel
US20150110603A1 (en) 2013-10-17 2015-04-23 Rohr, Inc. Acoustic structural panel with slanted core
US20150284945A1 (en) 2014-04-04 2015-10-08 The Boeing Company Pyramid waffle core structure and method of fabrication
US20150367953A1 (en) 2014-06-23 2015-12-24 Rohr, Inc. Acoustic liner
US20160312709A1 (en) 2015-01-29 2016-10-27 Rohr, Inc. Acoustic structural panel with herringbone core
CN104723616A (zh) 2015-03-17 2015-06-24 西安交通大学 一种轻质正交波纹夹芯复合结构及其制备方法
US20170225764A1 (en) * 2016-02-10 2017-08-10 Rohr, Inc. Structural, cellular core with corrugated support walls
US20170229106A1 (en) 2016-02-10 2017-08-10 Rohr, Inc. Acoustic panel with angled corrugated core structures
US9704467B1 (en) 2016-04-15 2017-07-11 Rohr, Inc. Acoustic panel with corrugated baffles and septums
US20170301334A1 (en) 2016-04-15 2017-10-19 Rohr, Inc. Acoustic panel with vertical stiffeners
US20180142621A1 (en) 2016-11-18 2018-05-24 Rohr, Inc. Acoustic panel with sidewall stringers
US20180229829A1 (en) 2017-02-14 2018-08-16 Rohr, Inc. Method for forming a structural panel

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
EP search report for EP19166905.0 dated Sep. 16, 2019.
EP search report for EP19216015.8 dated May 26, 2020.
EP search report for EP19216189.1 dated May 26, 2020.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11433990B2 (en) * 2018-07-09 2022-09-06 Rohr, Inc. Active laminar flow control system with composite panel
US12479201B2 (en) 2022-07-08 2025-11-25 Rohr, Inc. Forming pattern for cellular core by folding material

Also Published As

Publication number Publication date
EP3553771B1 (de) 2023-05-31
EP3553771A1 (de) 2019-10-16
US20190300188A1 (en) 2019-10-03
CN110341931A (zh) 2019-10-18

Similar Documents

Publication Publication Date Title
US11242822B2 (en) Structured panel with multi-panel structure(s)
US9761216B2 (en) Acoustic panel with angled corrugated core structures
EP3324400B1 (de) Akustikplatte mit seitenwandholmen
US9704467B1 (en) Acoustic panel with corrugated baffles and septums
US9978354B2 (en) Acoustic panel with vertical stiffeners
US11572850B2 (en) Acoustic panel with one or more structural stiffeners
EP3422342B1 (de) Akustikplatte mit faltkammer
US9764818B2 (en) Structural, cellular core with corrugated support walls
US10316755B2 (en) Acoustic panel with sidewall stringers
US9708930B2 (en) Multi-degree of freedom acoustic panel
US11066147B2 (en) Structured panel with integrated skin and sidewalls
US10906659B2 (en) Structured panel with structural reinforcement(s)
US20240271572A1 (en) Acoustic panel with multiple layer corrugated core

Legal Events

Date Code Title Description
FEPP Fee payment procedure

Free format text: ENTITY STATUS SET TO UNDISCOUNTED (ORIGINAL EVENT CODE: BIG.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

AS Assignment

Owner name: ROHR, INC., CALIFORNIA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GURVICH, MARK R.;ZAFIRIS, GEORGIOS S.;ANDERSON, JEFFREY A.;AND OTHERS;SIGNING DATES FROM 20180329 TO 20180405;REEL/FRAME:045492/0901

STPP Information on status: patent application and granting procedure in general

Free format text: AWAITING TC RESP., ISSUE FEE NOT PAID

STPP Information on status: patent application and granting procedure in general

Free format text: PUBLICATIONS -- ISSUE FEE PAYMENT VERIFIED

STCF Information on status: patent grant

Free format text: PATENTED CASE

CC Certificate of correction
MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 4